5340783064

PANELS

Die Stabilitatsgrenze eines gekrUmmten plattenstreifens bei fcean-spruchung durch schub-und lUngskr&fte, von A. Kroim. Luft-fahrtforschung, Berlin, Qct. 10, 1938, v. 15, no. 10-11, p. 517-26. diagrs., tables.

Elastic stability of curved piąte under axial thrusts, by S. C. Redshaw. Journal of the R.A.S., London, June 1930, v. 42, no. 330, p. 536-55. bibliog., illus.

Calculation of load distribution in stiffened cylindrical shells, by H. Ebner and H. Kttller* Washington, 1938.    62 p.

(N.A.C.A. Technical memorandums no. 866) (From Luftfahrt-forschung, MUnchen, Dec. 20, 1937, v. 14, no. 12, p. 607-26)

Belastungsversuche mit einer versteiften kreiszylinderschale bei krafteinleitung an einzelnen punkten, von E. Schapitz und C. KrUraling. Luftfahrtforschung, MUnchen, Dec. 20, 1937, v. 14, no. 12, p. 593-06. diagrs., illus., tables.

Verhalten eines von schub- und druckkrSften beanspruchten

plattenstreifens oberhalb der beulgrenze, von A. Kromra und K. Margueri'©. Luftfahrtforschung, MUnchen, Dec. 20, 1937, v. 14, no. 12, p. 627-39. illus.

Stress distribution in stiffened panels under compression, by E. E. Sechler. Journal of the aeronautical Sciences,

New York, June 1937, v. 4, no. 8, p. 320-23. diagrs., illus

Uber die stabilitUt dUrmwandiger hohlzylinder und rechteckiger

bleche oberhalb der proportionalitStsgrenze, von W. Kaufmann Stahlbau, Berlin, Jan. 1, 1937, no. 1, p. 1-4. diagrs.

Effect of rivet spacing on stiffened thin sheet under compression, by W. Lavern Howlanó. Journal of the aeronautical Sciences, New York, Oct. 1936, v. 3, no. 12, p. 434-39. (AbsjtrĄct Journal of the R.A.S., London, Feb. 1937, p. 154)

New Light on the panel problem; allowable compression in alurninum alloy sheets, by E.J.A. Greenwood, Jr. Aviation, New York, Oct. 1936, v. 35, no. 10, p. 33-36. bibliog., diagrs.

Tests on stress distribution in reinforced panels, by Roland J. White and Hans M. Antz. Journal of the aeronautical Sciences, New York, Apr. 1956, v. 3, no. 6, p. 209-12. illus., tables.

Stressed-skin structures. Compression tests of panels with tubular stiffeners, by I.J. Gerard and B.G. Dickens.

London, H.M. Stat. off., 1936.    (A.R.C. R. & M. _no. 1830)

Skin deep (design and test data on stiffeners and stiffened

sheets, as well as cylindrical structures), by J.S, Newell. Aviation, New York, Nov.-Dec. 1935, v. 34, no. 11-12, p. 18-20; 19-20. diagrs., tables*